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Influences of the compressibility on aerodynamic characteristics of profile under the transonic flow theory

Chia sẻ: Hung Hung | Ngày: | Loại File: PDF | Số trang:10

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Numerical results show that the local compressibility depends on not only the speed but also the incidence. At arather great angle of attack, local supersonic regions can appear with free Mach numbers in the order of 0.3 - the Mach number is normally considered as a speed of incompressible flows.

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Nội dung Text: Influences of the compressibility on aerodynamic characteristics of profile under the transonic flow theory

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